EP2879258B1 - Système de gestion de puissance d'aéronef et procédé de gestion d'alimentation dans un aéronef - Google Patents

Système de gestion de puissance d'aéronef et procédé de gestion d'alimentation dans un aéronef Download PDF

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Publication number
EP2879258B1
EP2879258B1 EP13194913.3A EP13194913A EP2879258B1 EP 2879258 B1 EP2879258 B1 EP 2879258B1 EP 13194913 A EP13194913 A EP 13194913A EP 2879258 B1 EP2879258 B1 EP 2879258B1
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EP
European Patent Office
Prior art keywords
primary
bus bar
electrical equipment
power supply
load
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Active
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EP13194913.3A
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German (de)
English (en)
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EP2879258A1 (fr
Inventor
Sebastian Scheffler
Frank LEUENBERGER
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Airbus Operations GmbH
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Airbus Operations GmbH
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Priority to EP13194913.3A priority Critical patent/EP2879258B1/fr
Priority to US14/552,593 priority patent/US9787092B2/en
Publication of EP2879258A1 publication Critical patent/EP2879258A1/fr
Application granted granted Critical
Publication of EP2879258B1 publication Critical patent/EP2879258B1/fr
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Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/14—Balancing the load in a network
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/12—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load
    • H02J3/14—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D2011/0053—Cabin passenger reading lights
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2221/00—Electric power distribution systems onboard aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2231/00—Emergency oxygen systems
    • B64D2231/02—Supply or distribution systems
    • B64D2231/025—Oxygen masks; Mask storages; Features related to mask deployment
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
    • H02J2310/40—The network being an on-board power network, i.e. within a vehicle
    • H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts

Definitions

  • the present invention pertains to an aircraft power management system and a method for managing power supply in an aircraft.
  • the electrical power generation system is furthermore designed to provide the sum of the maxima of all connected equipments.
  • electrical loads from equipments may occur at any time and independently from load requirements of other equipments. This allows for many electrical equipments to be activated at the same time, even if there is no specific use case tied to that situation.
  • the operation state of a vehicle such as an aircraft, precludes the activation of the cargo loading system during flight. But if an electrical equipment is activated by a human such as an passenger of an aircraft, the operational state of the aircraft is an insufficient parameter to predict the activation of such an equipment.
  • the document EP 1 387 460 A1 discloses a power supply arrangement for the galley of an airborne vehicle which utilizes control command provided by a control unit that manages the power consumption of galley equipment depending on individual operating conditions of the equipment.
  • the document DE 195 02 786 C2 discloses a method for protecting an electrical network from overload by inhibiting the activation of electrical equipment which would else cause an overload.
  • EP 2 579 412 A1 discloses a system and method for automated management of electric power supply for aeronautical applications.
  • the document US 2009/152942 A1 discloses a method to provide dynamic electrical power management which may minimize the potential for overload conditions and may ensure that system performance limits are maintained.
  • the method may dynamically limit the primary load system power draw in response to the net power draw of all other electrical power users on an aircraft which may ensure that the total power levels remain below critical limits.
  • the method may also provide predictive controls to handle rapid load transients. Additionally, if vital functions are not being met, the method may shed other selected aircraft electrical loads which may ensure that adequate power is provided to the primary load system.
  • the document US 2007/241614 A1 discloses a vehicle power bus control system including a control module having a communication interface and a device having a communication interface for communicating with the control module wherein the control module is adapted to transfer at least one electrical limit value to the device, and wherein the device is adapted to act in response to the electrical limit value to self-regulate an electrical quantity associated with the device.
  • an aircraft power management system comprising an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load and a bus bar switch, the primary load being coupled to the first power supply bus bar, and the bus bar switch being configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, and at least one tertiary electrical equipment including a tertiary load being coupled to the first power supply bus bar downstream of the at least one primary electrical equipment in parallel to the primary load, characterized in that the at least one primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar downstream of the at least one primary electrical equipment, if the monitored power demand of the primary load exceeds a primary threshold, the primary threshold being zero.
  • the object is solved by a method for managing power supply in an aircraft having a power management system of the invention, the method comprising operating the tertiary load of the tertiary electrical equipment, and monitoring the power demand of the primary load of the primary electrical equipment, characterized by selectively deactivating the first power supply bus bar downstream of the at least one primary electrical equipment, if the monitored power demand of the primary load exceeds a primary threshold, the primary threshold being zero.
  • the object is further solved by a hatrack for an aircraft comprising a power management system according to an embodiment of the invention.
  • One idea of the present invention is to localize power management function in or with electrical components that have a function of higher or equal criticality for the aircraft than the criticality level of power management itself.
  • the aircraft operational state and the system dynamics are subject to the principles of mutually exclusive activation.
  • the main concept involves exploiting the knowledge that simultaneous activation of at least two loads is either impossible to happen, i.e. natural mutually exclusive activation, or can be prohibited by the power management without significant loss in performance of the two loads, i.e. forced mutually exclusive activation.
  • the power management system may further comprise at least one secondary electrical equipment including a secondary load and a bus bar switch, the secondary load being coupled to the first power supply bus bar downstream of the primary electrical equipment in parallel to the primary load, and the bus bar switch of the secondary electrical equipment being configured to selectively deactivate the first power supply bus bar downstream of the secondary electrical equipment.
  • at least one secondary electrical equipment including a secondary load and a bus bar switch, the secondary load being coupled to the first power supply bus bar downstream of the primary electrical equipment in parallel to the primary load, and the bus bar switch of the secondary electrical equipment being configured to selectively deactivate the first power supply bus bar downstream of the secondary electrical equipment.
  • the at least one secondary electrical equipment may further include a load monitoring device configured to monitor the power demand of the secondary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar downstream of the secondary electrical equipment, if the monitored power demand of the secondary load exceeds a secondary threshold.
  • a load monitoring device configured to monitor the power demand of the secondary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar downstream of the secondary electrical equipment, if the monitored power demand of the secondary load exceeds a secondary threshold.
  • the power management system may further comprise a second power supply bus bar coupled to the power supply input in parallel to the first power supply bus bar, at least one additional primary electrical equipment including a primary load and a bus bar switch, the primary load being coupled to the second power supply bus bar, and the bus bar switch being configured to selectively deactivate the second power supply bus bar downstream of the at least one additional primary electrical equipment, and at least one additional tertiary electrical equipment including a tertiary load being coupled to the second power supply bus bar downstream of the at least one additional primary electrical equipment in parallel to the primary load of the at least one additional primary electrical equipment, wherein the at least one additional primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the second power supply bus bar downstream of the at least one additional primary electrical equipment, if the monitored power demand of the primary load exceeds a primary threshold.
  • the at least one additional primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the
  • Power management systems within the meaning of the present application may include any group or installation of multiple different electrical equipments being supplied with power from a common power supply bus.
  • power management systems within the meaning of the present application may advantageously be employed in space limited environments, especially in airborne vehicles.
  • Power management systems within the meaning of the present application may comprise, for example, lavatories, hatracks, aircraft seats, aircraft galleys, door actuation systems, cargo load bays and similar systems within an aircraft and/or the passenger cabin of an aircraft.
  • Fig. 1 schematically shows an illustration of an exemplary power management system 100 within an aircraft or airborne vehicle.
  • the power management system 100 comprises an electrical power supply input SV which is configured to be coupled to an electrical power supply.
  • the electrical power supply may in particular be adapted to the supply demand of the equipments in the power management system 100, i.e. in supply voltage level and supply voltage type (AC or DC).
  • the power supply input SV feeds a main power supply bus bar B which is turn is coupled to a first power supply bus bar B1.
  • the first power supply bus bar B1 is configured to support the power supply for a first group G1 of equipments or electrical devices, generally denoted with reference signs 10, 20 or 30 depending on the respective criticality of their electrical main function.
  • the electrical equipments 10 with the highest criticality level of their respective main electrical function are hereinforth denoted as primary electrical equipment 10.
  • the electrical equipments 20 with a medium or intermediate criticality level of their respective main electrical function are hereinforth denoted as secondary electrical equipment 20.
  • the electrical equipments 30 with the lowest criticality level of their respective main electrical function are hereinforth denoted as tertiary electrical equipment 30.
  • the first power supply bus bar B1 is coupled via an equipment terminal input 1 to the primary electrical equipment 10 of the first equipment group G1.
  • the equipment group G1 may be an assembly of electrical equipments in a hatrack.
  • the primary electrical equipment 10 comprises a primary load 2 coupled in parallel to the first power supply bus bar B1.
  • the primary load 2 may for example be an oxygen mask deployment system of a hatrack.
  • a bus bar switch 4 is coupled into the bus bar, the bus bar switch 4 being configured to selectively deactivate the first power supply bus bar B1 downstream of the primary electrical equipment 10 of the first equipment group G1.
  • the primary electrical equipment 10 further includes a load monitoring device 3 which is coupled to both the primary load 2 and the bus bar switch 4 is configured to monitor the power demand of the primary load 2, for example by monitoring a drawn current of the primary load 2 or by detecting an activated operational state of the primary load 2, and to output a deactivation signal to the bus bar switch 4.
  • the deactivation signal is configured to selectively deactivate the first power supply bus bar B1, if the monitored power demand of the primary load 2 exceeds a primary threshold.
  • the primary threshold may for example be in particular zero, i.e. if the primary load 2 draws power from the first bus bar B1 at all, the equipments downstream of the primary electrical equipment 10 are cut off from the power supply input SV immediately.
  • the tertiary electrical equipment 30 likewise comprises an equipment input terminal 1, which is coupled to the first power supply bus bar B1.
  • the tertiary electrical equipment 30 is the last equipment coupled to the first power supply bus bar B1, thus, the tertiary electrical equipment 30 does not need to comprise the bus bar switch 4 and the load monitoring device 3.
  • the tertiary electrical equipment 30 in a hatrack may for example be the passenger reading light system with the tertiary load 2 being the passenger reading lights.
  • the primary load 2 of the primary electrical equipment 10 may be a oxygen mask deployment device and the primary load 2 of the tertiary electrical equipment 30 may be the passenger reading lights in the hatrack.
  • the oxygen masks are only used in case of cabin decompression.
  • the oxygen containers are classified as safety essential equipment. Consequently, the oxygen mask deployment device needs to be taken into account for power supply independently of the flight situation.
  • the passenger reading lights need to be generally available for the whole duration of the flight, so that passengers can switch them on and off on demand.
  • the passenger reading lights are considered to be not essential for the safety of the aircraft.
  • the passenger reading lights may be deactivated without further significant effect for the safety of the aircraft.
  • the oxygen mask deployment device and the passenger reading lights may be considered as mutually exclusive components which can be shared on the first power supply bus bar B1.
  • the oxygen mask deployment system In normal flight operation, the oxygen mask deployment system is not used, but its primary load 2 is available all the time and can be shared with the passenger reading lights.
  • the oxygen mask deployment device demands power and the load monitoring device 3 of the primary electrical equipment 10 emits a deactivation signal to the bus bar switch 4. Then, the passenger reading light system is disconnected from the first power supply bus bar B1 to reserve the full power supply capacities to the oxygen mask deployment device.
  • the equipment with the higher criticality hosts the power management function to avoid that the equipment with a lower criticality can contribute to a safety relevant failure.
  • the power supply system does not need to serve both the primary and the tertiary electrical equipments of the same equipment group at the same time.
  • the maximum load demand of the system with the higher load demand needs to be taken into account for the power generation system instead of the sum of the maximum load demands of both equipments.
  • the load with lower criticality may under normal flight conditions still be treated like a system with higher criticality since the whole power supply bus does not need to be shed in overload situations. This enhances the availability of lower criticality systems without compromising the stability of the whole power generation system.
  • the oxygen mask deployment system is rarely used.
  • most of the electrical connections in the cabin related to the oxygen mask deployment system remain unpowered most of the time. Degradation induced failure of the wires and/or connections would therefore remain hidden until the system is actually activated.
  • the power management system 100 the wires and connections to the oxygen mask deployment system are actually under constant use of the passenger reading lights. Therefore, a wire fault may readily be detected under noncritical safety conditions. This relaxes the requirements on the safety check intervals by a lot.
  • the power management system 100 may include in the first power supply bus bar B1 at least one secondary electrical equipment 20 including a secondary load 2 and a bus bar switch 4, the secondary load 2 being coupled in parallel to the first power supply bus bar B1 downstream of the primary electrical equipment 10.
  • the equipment input terminal 1 is coupled to the equipment output terminal 5 of the previous electrical equipment, in this the primary electrical equipment.
  • the bus bar switch 4 of the secondary electrical equipment 20 is configured to selectively deactivate the first power supply bus bar B1 downstream of the secondary electrical equipment 20.
  • the secondary electrical equipment 20 further includes a load monitoring device 3 configured to monitor the power demand of the secondary load 2 and to output a deactivation signal to the respective bus bar switch 4 for selectively deactivating the first power supply bus bar B1 downstream of the secondary electrical equipment 20, if the monitored power demand of the secondary load 2 exceeds a secondary threshold.
  • a load monitoring device 3 configured to monitor the power demand of the secondary load 2 and to output a deactivation signal to the respective bus bar switch 4 for selectively deactivating the first power supply bus bar B1 downstream of the secondary electrical equipment 20, if the monitored power demand of the secondary load 2 exceeds a secondary threshold.
  • any number of secondary electrical equipments 20 may be coupled in series between the primary electrical equipment 10 and the tertiary electrical equipment 30, with the criticality of the ones downstream of the first power supply bus bar B1 decreasing with respect to the previous ones in series.
  • loads are not designed to be put into mutually exclusive activation. Therefore, it may be possible to provide additional power supply bus bars Bn coupled to the power supply input SV in parallel to the first power supply bus bar B1, which may be similarly built-up with at least one additional primary electrical equipment 10 and at least one additional tertiary electrical equipment 30 as explained above. That way, multiple equipment groups G1 to Gn may be assembled, each with a respective primary electrical equipment 10 of higher criticality, associated with tertiary electrical equipments 30 of lower criticality. Again, any number of secondary electrical equipments 20 may be optionally coupled in series between the primary electrical equipment 10 and the tertiary electrical equipments 30.
  • the electrical equipments 10, 20 or 30 or different groups G1 to Gn may be associated logically in criticality level groups L1, L2 to Lm, depending on the number m of different criticality levels overall.
  • Fig. 2 schematically illustrates the power management architecture of Fig. 1 for a single equipment group Gi.
  • the equipment group Gi may comprise multiple secondary electrical equipments 20 and tertiary electrical equipments 30 which have the same criticality level. Those equipments can be arranged in parallel to each other within the equipment group Gi by coupling their respective equipment input terminals in parallel to the equipment output terminal 5 of the primary electrical equipment 10. Again, any number of secondary and tertiary electrical equipments may be employed within any one equipment group Gi.
  • Fig. 3 shows a schematic illustration of a method M for managing power supply in an aircraft, specifically utilizing a power management system 100 as depicted in Fig. 1 and 2 .
  • the method M comprises as a first step M1 operating the tertiary load 2 of the tertiary electrical equipment 30.
  • a second step M2 the power demand of the primary load 2 of the primary electrical equipment 10 is monitored.
  • the first power supply bus bar B, B1 is selectively deactivated.

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Supply And Distribution Of Alternating Current (AREA)
  • Aviation & Aerospace Engineering (AREA)

Claims (6)

  1. Système de gestion d'énergie (100) pour un aéronef, comprenant :
    une entrée d'alimentation électrique (SV) configurée pour être couplée à une alimentation électrique ;
    une première barre omnibus d'alimentation (B ; B1) couplée à l'entrée d'alimentation (SV) ;
    au moins un équipement électrique primaire (10) comprenant une charge primaire (2) et un commutateur de barre omnibus (4), la charge primaire (2) étant couplée à la première barre omnibus d'alimentation (B ; B1), et le commutateur de barre omnibus (4) étant configuré pour désactiver de manière sélective la première barre omnibus d'alimentation (B ; B1) en aval dudit au moins un équipement électrique primaire (10) ; et
    au moins un équipement électrique tertiaire (30) comprenant une charge tertiaire (2) qui est couplée à la première barre omnibus d'alimentation (B ; B1) en aval dudit au moins un équipement électrique primaire (10) parallèlement à la charge primaire (2) ;
    caractérisé en ce que ledit au moins un équipement électrique primaire (10) comprend en outre un dispositif de surveillance de charge (3) configuré pour surveiller la demande d'énergie de la charge primaire (2) et pour fournir un signal de désactivation au commutateur de barre omnibus (4) pour désactiver de manière sélective la première barre omnibus d'alimentation (B ; B1) en aval dudit au moins un équipement électrique primaire (10), si la demande d'énergie surveillée de la charge primaire (2) dépasse un seuil primaire, le seuil primaire étant zéro.
  2. Système de gestion d'énergie (100) selon la revendication 1, comprenant en outre :
    au moins un équipement électrique secondaire (20) comprenant une charge secondaire (2) et un commutateur de barre omnibus (4),
    la charge secondaire (2) étant couplée à la première barre omnibus d'alimentation (B ; B1) en aval de l'équipement électrique primaire (10) parallèlement à la charge primaire (2), et le commutateur de barre omnibus (4) de l'équipement électrique secondaire (20) étant configuré pour désactiver de manière sélective la première barre omnibus d'alimentation (B ; B1) en aval de l'équipement électrique secondaire (20).
  3. Système de gestion d'énergie (100) selon la revendication 2, dans lequel ledit au moins un équipement électrique secondaire (20) comprend en outre un dispositif de surveillance de charge (3) configuré pour surveiller la demande d'énergie de la charge secondaire (2) et pour fournir un signal de désactivation au commutateur de barre omnibus (4) pour désactiver de manière sélective la première barre omnibus d'alimentation (B ; B1) en aval de l'équipement électrique secondaire (20), si la demande d'énergie surveillée de la charge secondaire (2) dépasse un seuil secondaire.
  4. Système de gestion d'énergie (100) selon l'une des revendications 1 à 3, comprenant en outre :
    une seconde barre omnibus d'alimentation (Bn) couplée à l'entrée d'alimentation (SV) parallèlement à la première barre omnibus d'alimentation (B ; B1) ;
    au moins un équipement électrique primaire supplémentaire (10) comprenant une charge primaire (2) et un commutateur de barre omnibus (4), la charge primaire (2) étant couplée à la seconde barre omnibus d'alimentation (Bn), et le commutateur de barre omnibus (4) étant configuré pour désactiver de manière sélective la seconde barre omnibus d'alimentation (Bn) en aval dudit au moins un équipement électrique primaire supplémentaire (10) ; et
    au moins un équipement électrique tertiaire supplémentaire (30) comprenant une charge tertiaire (2) qui est couplée à la seconde barre omnibus d'alimentation (Bn) en aval dudit au moins un équipement électrique primaire supplémentaire (10) parallèlement à la charge primaire (2) d'au moins un équipement électrique primaire supplémentaire (10),
    dans lequel ledit au moins un équipement électrique primaire supplémentaire (10) comprend en outre un dispositif de surveillance de charge (3) configuré pour surveiller la demande d'énergie de la charge primaire (2) et pour fournir un signal de désactivation au commutateur de barre omnibus (4) pour désactiver de manière sélective de la seconde barre omnibus d'alimentation (Bn) en aval dudit au moins un équipement électrique primaire supplémentaire (10), si la demande d'énergie surveillée de la charge primaire (2) dépasse un seuil primaire.
  5. Rangement supérieur d'un aéronef, comprenant :
    un système de gestion d'énergie (100) selon l'une des revendications 1 à 4, dans lequel l'équipement électrique primaire (10) est un système de déploiement de masques à oxygène, et dans lequel l'équipement électrique tertiaire (30) est une lumière de lecture de passager.
  6. Procédé (M) de gestion d'alimentation dans un aéronef comportant un système de gestion d'énergie selon l'une des revendications 1 à 4, le procédé (M) comprenant :
    actionner (M1) la charge tertiaire (2) de l'équipement électrique tertiaire (30) ; et
    surveiller (M2), la demande d'énergie de la charge primaire (2) de l'équipement électrique primaire (10) ;
    caractérisé par
    désactiver de manière sélective (M3) la première barre omnibus d'alimentation (B ; B1) en aval dudit au moins un équipement électrique primaire (10), si la demande d'énergie surveillée de la charge primaire (2) dépasse un seuil primaire, le seuil primaire étant zéro.
EP13194913.3A 2013-11-28 2013-11-28 Système de gestion de puissance d'aéronef et procédé de gestion d'alimentation dans un aéronef Active EP2879258B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13194913.3A EP2879258B1 (fr) 2013-11-28 2013-11-28 Système de gestion de puissance d'aéronef et procédé de gestion d'alimentation dans un aéronef
US14/552,593 US9787092B2 (en) 2013-11-28 2014-11-25 Aircraft power management system and method for managing power supply in an aircraft

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Application Number Priority Date Filing Date Title
EP13194913.3A EP2879258B1 (fr) 2013-11-28 2013-11-28 Système de gestion de puissance d'aéronef et procédé de gestion d'alimentation dans un aéronef

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EP2879258A1 EP2879258A1 (fr) 2015-06-03
EP2879258B1 true EP2879258B1 (fr) 2016-07-13

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US9787092B2 (en) 2017-10-10
EP2879258A1 (fr) 2015-06-03
US20150148995A1 (en) 2015-05-28

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